Method for operating an aircraft

ABSTRACT

A method for operating an aircraft includes the steps of receiving guidance instructions and guidance parameters at a navigation computer, and transmitting automatic pilot instructions from the navigation computer to a flight control computer. The method also includes the steps of receiving control instructions and the automatic pilot instructions at the flight control computer, and generating operating commands at the flight control computer. In an automatic pilot mode, the operating commands are generated at the flight control computer based on the automatic pilot instructions.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a divisional application of published U.S. application Ser. No. 09/863,894, filed May 24, 2001, which claims priority under 35 U.S.C. § 119 to French Patent Application 00 06828, filed on May 29, 2000, the entire disclosure of both of which are incorporated herein by reference.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to aircraft with electrical fly-by-wire controls and, more particularly, to the architecture of the flight control system for such aircraft.

2. Discussion of the Background

It is known that an aircraft with electrical fly-by-wire controls has controls, such as sticks, ministicks, rudder bars, etc., equipped with electrical transducers so that they generate electrical control instructions which represent the action that a pilot exerts on them. It also includes a computer of flight control commands which, on the basis of the electrical control instructions generated by the controls and of control parameters originating, for example, from sensors, produces electrical operating commands that the flight control computer applies to actuators tasked with moving the control surfaces of the aircraft.

It is also commonplace for such an aircraft to have an automatic pilot capable, under certain circumstances, of piloting the aircraft in place of the pilot. As is also known, an automatic pilot consists essentially of a navigation computer and of a control computer. The navigation computer receives guidance instructions (indicated to it by the pilot) and guidance parameters (sent to it by sensors or by an inertial unit, for example), and from these guidance instructions and parameters produces automatic pilot instructions. For its part, the control computer converts these automatic pilot instructions into commands for operating the automatic pilot, which it applies to the actuators of the control surfaces of the aircraft.

Depending on the known embodiments of automatic pilots, the commands for operating the automatic pilot are applied to the actuators either directly or via the flight control computer. In the latter case, it will be noted that the flight control computer receives, from the automatic pilot, the commands for operating the automatic pilot which have already been fully produced and that in consequence its role amounts simply to transmitting the automatic pilot control commands unmodified.

Whichever of these two embodiments is on board the aircraft, it must also, however, be pointed out that, in such a known architecture, it is necessary to provide two control functions, namely one for the flight control computer and the other for the automatic pilot. Aside from the fact that this gives rise to significant costs, it may happen, owing to constraints of the system, that the control functions differ, particularly as regards the calculation power, the acquisition of parameters, the monitoring, etc. It is therefore compulsory to develop and to validate two control functions. In addition, a structure such as this does not make it possible to minimize the delays between the inertial information and the operating commands given by the automatic pilot to the control surfaces.

SUMMARY OF THE INVENTION

An object of the present invention is to overcome these drawbacks.

To this end, according to an embodiment of the invention, an aircraft with electrical fly-by-wire controls, equipped with control surfaces capable of being moved by electrically operated actuators, includes controls and a flight control computer. The controls are actuated by a pilot and generate electrical control instructions which are sent to the flight control computer. The flight control computer generates, from the electrical control instructions and from control parameters, operating commands sent to the actuators to move the control surfaces.

The aircraft also includes an automatic pilot capable of piloting the aircraft in place of the pilot and exerting a navigation function making it possible to produce automatic pilot instructions from the guidance instructions and guidance parameters sent to it. The automatic pilot can also exert a control function which consists in producing, from the automatic pilot instructions, automatic pilot operating commands sent to the actuators to move the control surfaces.

The automatic pilot can consist exclusively of calculation means producing the automatic pilot instructions from the guidance instructions and the guidance parameters. The calculation means are connected directly to the flight control computer so as to send the automatic pilot instructions to the latter. The flight control computer, from the automatic pilot instructions, produces the automatic pilot operating commands and sends these commands to the actuators to cause them to move the control surfaces accordingly.

Thus, according to the present invention, the control computer of the automatic pilot is eliminated and it is the flight control computer which fulfils the control function of the automatic pilot. The invention therefore makes it possible to develop and validate just one control function, the latter being embedded in the flight control computer. In addition it makes it possible to minimize the delay between the inertial information and the commands issued to the control surfaces by the automatic pilot. Furthermore, it also offers the possibility of making the responses of the aircraft under manual piloting consistent with those with the automatic pilot in operation.

As a preference, in order to simplify the structure of the flight control computer as far as possible, the electrical control instructions from the controls and the automatic pilot instructions from the calculation means of the automatic pilot are, by pairs, of the same nature. For example, the calculation means of the automatic pilot produce, from the guidance instructions and the guidance parameters, three automatic pilot instructions which correspond respectively to a commanded vertical load factor, to a commanded roll rate and to a commanded yaw. The controls generate three electrical control instructions which are respectively consistent with a commanded vertical load factor, with a commanded roll rate and with a commanded yaw.

BRIEF DESCRIPTION OF THE DRAWINGS

The figures of the appended drawing will make it easy to understand how the invention may be embodied. In these figures, identical references denote elements which are similar.

FIGS. 1 and 2 schematically illustrate two known architectures of an aircraft electrical fly-by-wire system.

FIG. 3 schematically illustrates the architecture of the electrical fly-by-wire system according to the present invention.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

The known architecture 1 of an electrical fly-by-wire system for an aircraft (not depicted) essentially includes controls 2 including elements 2A such as ministicks, rudder bars, etc., intended to be actuated by a pilot (not depicted) and associated with transducers 2B generating electrical control instructions representative of the movements of the elements 2A. A flight control computer 3 receives in the usual way, via links 4, the electrical control instructions generated by the controls 2, and via links 5 receives control parameters from sensors, other computers, etc. and which, from the electrical control instructions and the control parameters, generates operating commands. An actuators 6 receives the operating commands via links 7 and which move the control surfaces 8 of the aircraft accordingly, for example in rotation about axes X-X. An automatic pilot 9 includes a navigation computer 9A and a control computer 9B.

The navigation computer 9A receives, from a device 10, guidance instructions which are put up by the pilot and transmitted thereto by links 11. It also receives guidance parameters sent to it from the sensors, other computers, etc. by lines 12. From the guidance instructions and the guidance parameters, the navigation computer 9A produces automatic pilot instructions which it sends to the control computer 9B via links 13. The control computer 9B, from these automatic pilot instructions, produces commands for operating the automatic pilot, which it sends to the actuators 6, via links 14, so as to move the control surfaces 8.

In an alternative form of embodiment 15, which is also known and shown in FIG. 2, all of the elements 2 to 13 described with reference to FIG. 1 can again be seen. The only difference compared with the architecture of the latter figure lies in the fact that the commands for operating the automatic pilot, produced by the control computer 9B, instead of being sent directly to the actuators 6 via the links 14, are sent there indirectly via the flight control computer 3. What actually happens is that links 16 connect the outputs of the control computer 9B to the flight control computer 3. Thus, the latter receives, from the control computer 9B, the commands for operating the automatic pilot which have been fully produced, and transmits them, without modifying them, to the actuators 6, via the links 7. The transmission through the flight control computer 3 is passive, and is equivalent to that performed by the lines 14 in FIG. 1.

The architecture 17 according to the present invention and illustrated schematically in FIG. 3 includes all the elements 2 to 8 and 10 to 12 described hereinabove. By contrast, the control computer 9B and the associated links 13, 14, 16 have been omitted.

In the architecture 17, the automatic pilot instructions produced by the navigation computer 9A are sent directly to the flight control computer 3 by links 18. From these automatic pilot instructions, the flight control computer 3, in a similar way to what occurs with the electrical control instructions from the controls 2, produces commands for operating the automatic pilot, which it sends to the actuators 6 via the links 7.

From guidance (heading, vertical speed, altitude, etc.) instructions sent to it by the device 10, the navigation computer 9A calculates three automatic pilot instructions, namely a commanded vertical load factor, a commanded roll rate and a commanded yaw. The latter instructions are sent, via the links 16, to the flight control computer 3 which produces the automatic turning commands for the control surfaces 8 (elevator, stabilizer, ailerons, rudder, etc.).

Moreover, the controls 2 (sticks, rudder bars, etc.) produce control instructions which are respectively consistent with a commanded vertical load factor, a commanded roll rate and a commanded yaw. These control instructions are also sent to the flight control computer 3, which produces the turn commands for the control surfaces 8. 

1. A method for operating an aircraft, comprising the steps of: receiving guidance instructions and guidance parameters at a navigation computer; transmitting automatic pilot instructions from said navigation computer to a flight control computer; receiving control instructions and said automatic pilot instructions at said flight control computer; and in an automatic pilot mode, generating a first plurality of operating commands based on said automatic pilot instructions at said flight control computer.
 2. The method of claim 1, further comprising, in a manual pilot mode, the step of generating a second plurality of operating commands based on said control instructions at said flight control computer.
 3. The method of claim 1, further comprising the step of receiving control parameters at said flight control computer.
 4. The method of claim 1, wherein said first and second pluralities of operating commands are based on a single control function.
 5. The method of claim 4, further comprising the step of validating said single control function.
 6. The method of claim 4, wherein said single control function is embedded in said flight control computer.
 7. The method of claim 1, further comprising the step of generating said automatic pilot instructions at said navigation computer based on said guidance instructions and on said guidance parameters.
 8. The method of claim 7, wherein said automatic pilot instructions correspond in nature to said control instructions.
 9. The method of claim 8, wherein said automatic pilot instructions and said control instructions correspond to a commanded vertical load factor.
 10. The method of claim 8, wherein said automatic pilot instructions and said control instructions correspond to a commanded roll rate.
 11. The method of claim 8, wherein said automatic pilot instructions and said control instructions correspond to a commanded yaw.
 12. The method of claim 1, wherein the step of transmitting said automatic pilot instructions from said navigation computer to said flight control computer is performed so that said flight control computer receives said automatic pilot instructions directly from said navigation computer without an intermediate step.
 13. A method for operating an aircraft, comprising the steps of: transmitting automatic pilot instructions from a navigation computer directly to a flight control computer; receiving control instructions and said automatic pilot instructions at said flight control computer; in an automatic pilot mode, generating a first plurality of operating commands based on said automatic pilot instructions at said flight control computer; and in a manual pilot mode, generating a second plurality of operating commands based on said control instructions at said flight control computer.
 14. The method of claim 13, wherein said first and second pluralities of operating commands are based on a single control function.
 15. The method of claim 14, further comprising the step of validating said single control function.
 16. The method of claim 14, wherein said single control function is embedded in said flight control computer. 